CN115597881B - Method for verifying starting and slow running of core engine of aircraft engine - Google Patents
Method for verifying starting and slow running of core engine of aircraft engine Download PDFInfo
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- CN115597881B CN115597881B CN202211577744.0A CN202211577744A CN115597881B CN 115597881 B CN115597881 B CN 115597881B CN 202211577744 A CN202211577744 A CN 202211577744A CN 115597881 B CN115597881 B CN 115597881B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/40—Engine management systems
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- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The application belongs to the field of testing of aircraft engines, and provides a method for starting and checking a slow vehicle of an aircraft engine core machine.
Description
Technical Field
The application belongs to the technical field of testing of aero-engines, and particularly relates to a method for verifying starting and slow running of a core engine of an aero-engine.
Background
The core engine of the aircraft engine consists of a gas compressor, a combustion chamber and a turbine, works under high-temperature and high-pressure conditions at high rotating speed, and is a key component combination which has the worst working conditions in the aircraft engine and has the greatest influence on the performance of the aircraft engine.
After the design of the core engine of the aero-engine is completed, whether the performance, the function and the durability of the core engine reach design expectations or not and whether the adopted new design, the new material and the new process are feasible or not are verified, and on the basis of verifying the mature core engine, the aero-engines with different bypass ratios and different purposes are developed in series by matching low-pressure systems with different flow rates, so that the development risk is reduced, and the development period is shortened.
The method mainly comprises the steps of verifying an aircraft engine core machine, assembling an air passage, an outer duct and a spray pipe for the core machine on a rack, and carrying out related test verification, wherein starting and slow vehicle verification are the first test run of the core machine, and are the basis for verifying the core machine, and the items needing verification are various, including the aspects of determining ignition rotating speed, flameout boundary, slow vehicle rotating speed, lowest oil supply quantity of accelerating oil, optimal deflation rule, checking a core machine pipeline system, working vibration conditions and the like.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only used for assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application in the case that there is no clear evidence that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine core engine start and slow vehicle verification method that overcomes or mitigates at least one of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
an aircraft engine core engine starting and slow vehicle verification method comprises the following steps:
normal temperature pressurization starting step: under the condition of normal temperature, the pressure at the inlet of the core machine is increased through the rack pressurizing device, and the core machine is operated by utilizing the pressure difference at the inlet and the outlet of the core machine;
determining the ignition rotating speed, the flameout boundary and the slow vehicle rotating speed: igniting the core machine, if the ignition is successful, gradually reducing the running speed of the core machine to obtain the ignition speed, a flameout boundary and the slow vehicle speed, and if the ignition is failed, re-performing the normal-temperature pressurized starting step;
slow vehicle running checking: the core machine is driven to run slowly, and the working vibration working condition of the core machine pipeline system and the core machine is checked;
a parking inspection step: parking check is carried out on the core machine, and the hardware state of the core machine is checked;
determining the minimum oil supply quantity of the accelerating oil: igniting the core machine under normal temperature and normal pressure, accelerating the core machine to a slow vehicle rotating speed by adjusting accelerating oil, and gradually reducing the oil supply amount of the accelerating oil under the condition of stable slow vehicle running to obtain the lowest oil supply amount of the accelerating oil;
and (3) test parking step: and operating the accelerator to a parking space to enable the core machine to park.
According to at least one embodiment of the application, in the method for starting the core engine and verifying the slow running of the aircraft engine, in the step of determining the ignition speed, the flameout boundary and the slow running speed, the ignition of the core engine is firstly performed at the ignition speed calculated by the theoretical starting simulation.
According to at least one embodiment of the application, in the aircraft engine core engine starting and slow vehicle verification method, in the step of determining the ignition speed, the flameout boundary and the slow vehicle speed, the success of ignition is judged by the increase of the exhaust temperature of the core engine.
According to at least one embodiment of the application, in the method for starting the aircraft engine core and verifying the slow vehicle, in the step of determining the ignition speed, the flameout boundary and the slow vehicle speed, the operation speed of the core engine is gradually reduced, and the operation speed of the core engine is gradually reduced by 1% of steps.
According to at least one embodiment of the application, in the method for starting the core engine of the aircraft engine and verifying the slow vehicle, in the step of determining the ignition speed, the flameout boundary and the slow vehicle speed, the slow vehicle speed is the lowest speed at which the core engine is maintained to operate.
According to at least one embodiment of the application, in the method for starting the aircraft engine core and verifying the slow turning, the slow turning checking step is to slow the core engine for at least five minutes.
According to at least one embodiment of the application, in the aircraft engine core start and slow vehicle verification method, in the acceleration oil minimum oil supply amount determination step, the acceleration oil supply amount is reduced by gradually reducing the acceleration oil supply amount in 5% steps.
According to at least one embodiment of the application, the method for aircraft engine core engine starting and slow vehicle verification further includes:
determining an optimal deflation rule: igniting the core machine under normal temperature and normal pressure, and searching the core machine to start the air release speed and air release amount to obtain the optimal air release rule.
According to at least one embodiment of the application, in the method for starting the core engine and verifying the slow vehicle of the aircraft engine, in the step of determining the optimal deflation law, the optimal deflation law takes the shortest core engine starting time and the lowest exhaust temperature as judgment conditions.
According to at least one embodiment of the application, the method for aircraft engine core engine starting and slow vehicle verification further includes:
measuring the starting torque of the core machine: and igniting the core machine under the conditions of normal temperature and normal pressure, and obtaining the starting torque of the core machine at each rotating speed by using a torque measuring device arranged on a rotor of the core machine.
The application has at least the following beneficial technical effects:
the method comprises the steps of increasing the inlet pressure of a core machine through a rack pressurizing device under the normal temperature condition, operating the core machine by utilizing the pressure difference between the inlet and the outlet of the core machine, igniting the core machine, obtaining the ignition rotating speed, the flameout boundary and the slow vehicle rotating speed in a mode of gradually reducing the operating speed of the core machine, then operating the core machine to slow the vehicle, checking the working vibration working condition of a pipeline system of the core machine and the core machine, further performing parking check on the core machine, checking the hardware state of the core machine, finally igniting the core machine under the normal temperature and normal pressure conditions, accelerating the core machine to the slow vehicle rotating speed by adjusting accelerating oil, gradually reducing the oil supply quantity of the accelerating oil under the condition of stable slow vehicle operation, obtaining the lowest oil supply quantity of the accelerating oil, operating an accelerator to a parking space, stopping the core machine, completing the verification of the core machine, few tests required to be carried out, high efficiency and effectively ensuring the safety of the core machine for testing the first time.
Drawings
FIG. 1 is a schematic diagram of an aircraft engine core start and slow vehicle verification method provided in an embodiment of the present application.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that devices or elements must have specific orientations, be constructed and operated in specific orientations, and that when the absolute position of an object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in the present application according to their specific situation.
The present application is described in further detail below with reference to fig. 1.
An aircraft engine core engine starting and slow vehicle verification method comprises the following steps:
normal temperature pressurization starting step: under the condition of normal temperature, the inlet pressure of the core machine is increased through the rack pressurizing device, and the core machine is operated by utilizing the pressure difference of the inlet and the outlet of the core machine;
determining the ignition rotating speed, the flameout boundary and the slow vehicle rotating speed: igniting the core machine, if the ignition is successful, gradually reducing the running speed of the core machine to obtain the ignition speed, a flameout boundary and the slow vehicle speed, and if the ignition is failed or the slow vehicle speed cannot run, re-performing the normal-temperature pressurization starting step;
slow vehicle running checking: the method comprises the following steps of enabling a core machine to run slowly, and checking the working vibration working conditions of a core machine pipeline system and the core machine, wherein the working vibration working conditions comprise checking whether dangerous vibration occurs to a core machine pipeline and key components thereof, whether vibration exceeds a limit and the like;
a parking inspection step: parking and checking the core machine, and checking the hardware state of the core machine, wherein the hardware state comprises checking whether screws fall off at the joints of the components of the core machine, whether structural members are damaged at the visible part of the core machine, and the like;
determining the minimum oil supply amount of the accelerated oil: igniting the core machine under the conditions of normal temperature and normal pressure, accelerating the core machine to the rotating speed of the slow vehicle by adjusting the accelerating oil, and gradually reducing the oil supply amount of the accelerating oil under the condition of stable running of the slow vehicle to obtain the lowest oil supply amount of the accelerating oil;
and (3) test parking step: and operating the accelerator to a parking space to enable the core machine to park.
For the method for starting and checking the slow running of the core engine of the aircraft engine disclosed in the above embodiment, as can be understood by those skilled in the art, the design is that firstly, under normal temperature conditions, the inlet pressure of the core engine is increased through the rack pressurizing device, the core engine is operated by using the pressure difference between the inlet and the outlet of the core engine, the core engine is ignited, the ignition speed, the flameout boundary and the slow running speed are obtained in a manner of gradually reducing the operation speed of the core engine, then, the core engine is made to run slowly, the working vibration working conditions of the pipeline system of the core engine and the core engine are checked, the core engine is further checked to stop, the hardware state of the core engine is checked, finally, under normal temperature and normal pressure conditions, the core engine is ignited, the core engine is accelerated to the slow running speed by adjusting the accelerating oil, under the condition of stable slow running of the core engine, the lowest oil supply amount of the accelerating oil is obtained, the accelerator is controlled to the parking space, the core engine is stopped, the core engine is checked, the core engine is finished, the test is few tests required to be carried out, the efficiency is high, and the highest state of the slow running of the core engine can be effectively guaranteed.
In some optional embodiments, in the method for aircraft engine core start and slow vehicle verification, in the step of determining the ignition speed, the flameout boundary and the slow vehicle speed, the ignition of the core engine is performed firstly at the ignition speed calculated by the theoretical start simulation.
In some optional embodiments, in the above method for starting and slowly turning the core engine of the aircraft engine, in the step of determining the ignition speed, the flameout boundary and the slowly turning speed, the success of ignition is determined by the increase of the exhaust temperature of the core engine.
In some optional embodiments, in the above method for starting and checking the aircraft engine core, in the step of determining the ignition speed, the flameout boundary, and the slow vehicle speed, the operation speed of the core is gradually reduced by 1% of a step size.
In some optional embodiments, in the method for aircraft engine core start and slow-start verification described above, in the step of determining the ignition speed, the flameout boundary, and the slow-start speed, the slow-start speed is the lowest speed at which the core engine is maintained to operate.
In some optional embodiments, in the method for aircraft engine core start and slow vehicle verification as described above, the slow vehicle operation checking step is to slow the core engine for at least five minutes.
In some optional embodiments, in the aircraft engine core start and slow vehicle verification method described above, in the step of determining the minimum supply amount of acceleration oil, the supply amount of acceleration oil is decreased, and the supply amount of acceleration oil is decreased gradually in 5% steps.
In some optional embodiments, in the above method for aircraft engine core engine start and slow vehicle verification, the method further includes:
determining an optimal deflation rule: igniting the core machine under the conditions of normal temperature and normal pressure, and searching the starting deflation rotating speed and the deflation amount of the core machine to obtain the optimal deflation rule.
In some optional embodiments, in the above method for verifying the start and slow stop of the core engine of the aircraft engine, in the step of determining the optimal deflation law, the optimal deflation law takes the shortest start time of the core engine and the lowest exhaust temperature as the determination conditions.
In some optional embodiments, in the above method for aircraft engine core engine start and slow vehicle verification, the method further includes:
measuring the starting torque of the core machine: and igniting the core machine under the conditions of normal temperature and normal pressure, and obtaining the starting torque of the core machine at each rotating speed by using a torque measuring device arranged on a rotor of the core machine.
The embodiments are described in a progressive mode in the specification, the emphasis of each embodiment is on the difference from the other embodiments, and the same and similar parts among the embodiments can be referred to each other.
Having thus described the present invention in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present invention is not limited to those specific embodiments, and that equivalent changes or substitutions of the related technical features may be made by those skilled in the art without departing from the principle of the present invention, and those technical aspects after such changes or substitutions will fall within the scope of the present invention.
Claims (10)
1. A method for verifying the starting and slow running of an aircraft engine core is characterized by comprising the following steps:
and (3) normal-temperature pressurized starting: under the condition of normal temperature, the pressure at the inlet of the core machine is increased through the rack pressurizing device, and the core machine is operated by utilizing the pressure difference at the inlet and the outlet of the core machine;
determining the ignition rotating speed, the flameout boundary and the slow vehicle rotating speed: igniting the core machine, if the ignition is successful, gradually reducing the running speed of the core machine to obtain the ignition speed, a flameout boundary and the slow vehicle speed, and if the ignition is failed, re-performing the normal-temperature pressurized starting step;
slow vehicle running checking: the core machine is driven to run slowly, and the pipeline system of the core machine and the working vibration working condition of the core machine are checked;
parking inspection: parking check is carried out on the core machine, and the hardware state of the core machine is checked;
determining the minimum oil supply amount of the accelerated oil: igniting the core machine under the conditions of normal temperature and normal pressure, accelerating the core machine to the rotating speed of the slow vehicle by adjusting the accelerating oil, and gradually reducing the oil supply amount of the accelerating oil under the condition of stable running of the slow vehicle to obtain the lowest oil supply amount of the accelerating oil;
and (3) test parking step: and operating the accelerator to a parking space to enable the core machine to park.
2. The aircraft engine core start and creep verification method of claim 1,
in the step of determining the ignition rotating speed, the flameout boundary and the slow vehicle rotating speed, the ignition of the core machine is firstly performed at the ignition rotating speed calculated by theoretical starting simulation.
3. The aircraft engine core start and creep verification method of claim 1,
in the step of determining the ignition rotating speed, the flameout boundary and the slow vehicle rotating speed, the success of ignition is judged by the rise of the exhaust temperature of the core engine.
4. The aircraft engine core engine starting and slow vehicle verification method according to claim 1,
in the step of determining the ignition rotating speed, the flameout boundary and the slow vehicle rotating speed, the operating speed of the core machine is gradually reduced, and the operating speed of the core machine is gradually reduced by 1% of step length.
5. The aircraft engine core engine starting and slow vehicle verification method according to claim 1,
in the step of determining the ignition rotating speed, the flameout boundary and the slow-moving rotating speed, the slow-moving rotating speed is the lowest rotating speed for maintaining the operation of the core machine.
6. The aircraft engine core start and creep verification method of claim 1,
in the slow vehicle running checking step, the core engine is slow vehicle running for at least five minutes.
7. The aircraft engine core start and creep verification method of claim 1,
in the step of determining the minimum oil supply amount of the accelerating oil, the oil supply amount of the accelerating oil is reduced, and the oil supply amount of the accelerating oil is gradually reduced by 5% step length.
8. The aircraft engine core start and creep verification method of claim 1,
further comprising:
determining an optimal deflation rule: igniting the core machine under the conditions of normal temperature and normal pressure, and searching the starting deflation rotating speed and the deflation amount of the core machine to obtain the optimal deflation rule.
9. The aircraft engine core start and creep verification method of claim 8,
in the step of determining the optimal deflation law, the optimal deflation law takes the shortest starting time of the core machine and the lowest exhaust temperature as judgment conditions.
10. The aircraft engine core start and creep verification method of claim 1,
further comprising:
measuring the starting torque of the core machine: and igniting the core machine under the conditions of normal temperature and normal pressure, and obtaining the starting torque of the core machine at each rotating speed by using a torque measuring device arranged on a rotor of the core machine.
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| CN202211577744.0A CN115597881B (en) | 2022-12-09 | 2022-12-09 | Method for verifying starting and slow running of core engine of aircraft engine |
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| CN202211577744.0A CN115597881B (en) | 2022-12-09 | 2022-12-09 | Method for verifying starting and slow running of core engine of aircraft engine |
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| CN115597881B true CN115597881B (en) | 2023-03-10 |
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